Load transfer devices at a stringer run-out

Abstract

Device for transferring in an stiffened skin of an aircraft component made of a composite material the load of an stringer ( 16 ) to the skin ( 11 ) in a stringer run-out zone, the stringer ( 16 ) being configured by a web ( 31 ) and a foot ( 33 ), comprising two brackets ( 40, 40′ ) configured as unitary parts by webs ( 41, 41′ ) to be joined to each side of the stringer web ( 31 ) in said run-out zone and feet ( 43, 43′ ) having a first section ( 45, 45′ ) to be joined to each side of the stringer foot ( 33 ) in said run-out zone and a second section ( 47, 47′ ) to be joined to the skin ( 11 ). An aircraft component made of a composite material using said device in the stringer run-outs

1 . A device for transferring in an stiffened skin of an aircraft component made of a composite material the load of an stringer ( 16 ) to the skin ( 11 ) in a stringer run-out zone, the stringer ( 16 ) being configured by a web ( 31 ) and a foot ( 33 ), characterized by comprising two brackets ( 40 ,  40 ′) configured as unitary parts by webs ( 41 ,  41 ′) to be joined to each side of the stringer web ( 31 ) in said run-out zone and feet ( 43 ,  43 ′) having a first section ( 45 ,  45 ′) to be joined to each side of the stringer foot ( 33 ) in said run-out zone and a second section ( 47 ,  47 ′) to be joined to the skin ( 11 ). 
     
     
         2 . A device according to  claim 1 , wherein the final section of said run-out zone the stringer ( 16 ) includes a tapered web ( 51 ) and a wider foot ( 53 ), and the brackets ( 40 ,  40 ′) also include tapered webs ( 55 ,  55 ′) and wider feet ( 57 ,  57 ′). 
     
     
         3 . A device according to  claim 1 , wherein said brackets ( 40 ,  40 ′) are made with a metallic material. 
     
     
         4 . An aircraft component made of a composite material comprising a skin ( 11 ) stiffened by a plurality of stringers configured by a web ( 31 ) and a foot ( 33 ), the component having at least one stringer ( 16 ) terminating at the proximity of another structural element in a run-out zone, characterized in that also comprise two brackets ( 40 ,  40 ′) for transferring the stringer load in said run-out zone to the skin ( 11 ), each bracket ( 40 ,  40 ′) being configured as an unitary part by a web ( 41 ,  41 ′) joined to each side of the stringer web ( 31 ) in said run-out zone and by a foot ( 43 ,  43 ′) having a first section ( 45 ,  45 ′) joined to each side of the stringer foot ( 33 ) in said run-out zone and a second section ( 47 ,  47 ′) joined to the skin ( 11 ). 
     
     
         5 . An aircraft component according to  claim 4 , wherein the final section of said run-out zone the stringer ( 16 ) includes a tapered web ( 51 ) and a wider foot ( 53 ), and the brackets ( 40 ,  40 ′) also include tapered webs ( 55 ,  55 ′) and wider feet ( 57 ,  57 ′). 
     
     
         6 . An aircraft component according to  claim 4 , wherein said joints are carried out with bolts. 
     
     
         7 . An aircraft component according to  claim 4 , wherein said brackets ( 40 ,  40 ′) are made with a metallic material. 
     
     
         8 . An aircraft component according to  claim 4 , wherein the component belongs to the torsion box of an aircraft wing.